Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(e431-il) EPPLER 431 AIRFOIL | Eppler E431 sailplane airfoil Max thickness 15.1% at 37.4% chord Max camber 4.2% at 42.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e431-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e431-il | 50,000 | 9 | 22.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e431-il | 50,000 | 5 | 19.8 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e431-il | 100,000 | 9 | 48.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e431-il | 100,000 | 5 | 46.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e431-il | 200,000 | 9 | 79.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e431-il | 200,000 | 5 | 76.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e431-il | 500,000 | 9 | 116 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e431-il | 500,000 | 5 | 109.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e431-il | 1,000,000 | 9 | 144.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e431-il | 1,000,000 | 5 | 130.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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